尾缘锯齿降低叶栅噪声的数值模拟

仝帆; 乔渭阳; 纪良; 王良锋; 许坤波; 王勋年

doi:10.13224/j.cnki.jasp.2016.04.016

尾缘锯齿降低叶栅噪声的数值模拟

doi: 10.13224/j.cnki.jasp.2016.04.016

1. 西北工业大学动力与能源学院, 西安 710072;
2. 中国空气动力研究与发展中心空气动力学国家重点实验室, 四川绵阳 621000

基金项目:

国家自然科学基金(51276149)

空气动力学国家重点实验室研究基金(SKLA20130201)

详细信息

作者简介:
仝帆(1990-),男,河北石家庄人,博士生,主要从事气动声学研究.

中图分类号: V231.3
计量
- 文章访问数: 1055
- HTML浏览量: 122
- PDF量: 604
- 被引次数: 0
出版历程
- 收稿日期: 2014-07-23
- 刊出日期: 2016-04-28

Numerical simulation on noise reduction for the cascade with trailing edge serrations

1. School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072;
2. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 采用大涡模拟与声类比的方法研究了尾缘锯齿对涡轮叶栅噪声的影响.设计了两种不同的尾缘锯齿,对比了Re=3.3×10⁵(基于叶片弦长与叶栅出口速度)下两种不同结构锯齿尾缘叶栅与直尾缘叶栅的声功率.结果表明:尾缘锯齿可以降低叶片吸力面边界层分离噪声约5dB,降低尾缘涡脱落噪声约10dB.进一步的研究表明,尾缘锯齿可以降低叶片尾缘附近表面的压力脉动幅值约50%,将展向相关尺度较大的涡破碎成展向相关尺度较小的涡,并消除尾缘脱落涡,这三者的综合作用使噪声得到降低.
- 尾缘锯齿 /
- 叶栅噪声 /
- 声类比 /
- 边界层分离噪声 /
- 脱落涡噪声
Abstract: Large eddy simulation and acoustic analogy were performed to investigate the effect of trailing edge serrations on the turbine cascade noise. Two different trailing edge were designed. Comparisons were made for the sound power of two different serrated trailing edge cascades and straight trailing edge cascade under Re=3.3×10⁵ (based on the blade chord and cascade outlet velocity).The result shows that the trailing edge serrations can reduce the blade suction surface boundary layer's separation noise by about 5dB and the trailing edge vortex shedding noise by about 10dB. Further investigation shows that trailing edge can reduce blade surface pressure fluctuation amplitude by about 50% near the trailing edge and change the vortexes of large spanwise correlation length into those of smaller spanwise correlation length. Furthermore, the trailing edge serrations can eliminate the trailing edge vortex shedding. The above three factors work jointly and contribute to the final noise reduction.
- trailing edge serration /
- cascade noise /
- acoustic analogy /
- boundary layer separation noise /
- vortex shedding noise

HTML

参考文献(28)

[1]	Brooks T F,Pope D S,Marcolini M A.Airfoil self-noise and prediction[R].Virginia,US:NASA Reference Publication 1218,1989.
[2]	Brooks T,Hodgson T.Trailing edge noise prediction from measured surface pressures[J].Journal of Sound and Vibration,1981,78(1):69-117.
[3]	Amiet R.Noise due to turbulent flow past a trailing edge[J]. Journal of Sound and Vibration,1976,47(3):387-393.
[4]	Amiet R.A note on edge noise theories[J].Journal of Sound and Vibration,1981,78(4):485-488.
[5]	Howe M S.Trailing edge noise at low Mach numbers[J].Journal of Sound and Vibration,1999,225(2):211-238.
[6]	Adams H.Patent application for a noiseless device:US,No.US2071012A[P].1937-02-22.
[7]	Graham R.The silent flight of owls[J].Journal of Royal Aeronautical Society,1934,286(1):837-843.
[8]	Lilley G M.A study of the silent flight of the owl[R].AIAA 98-2340,1998.
[9]	Bohn A.Edge noise attenuation by porous edge extensions[R].AIAA 76-80,1976.
[10]	Khorrami M,Choudhari M.Application of passive porous treatment to slat trailing edge noise[R].NASA TM-212416,2003.
[11]	Sarradj E,Geyer T.Noise generation by porous airfoils[R].AIAA-2007-3719,2007.
[12]	Finez1 A,Jondeau E,Roger M.Broadband noise reduction with trailing edge brushes[R].AIAA-2010-3980,2010.
[13]	Howe M S.Aerodynamic noise of a serrated trailing edge[J].Journal of Fluid and Structures,1991,5(1):33-45.
[14]	Howe M S.Noise produced by a sawtooth trailing edge[J].Journal of the Acoustical Society of America,1991,90(1):482-487.
[15]	Braun K A,van der Borg N J C M,Dassen A G M,et al.Serrated trailing edge noise[C]//Proceedings of European Wind Energy Conference.Nice,France:The European Wind Energy Association,1999:80-183.
[16]	Oerlemans S,Fisher M,Maeder T,et al.Reduction of wind turbine noise using optimized airfoils and trailing-edge serrations[R].AIAA-2008-2819,2008.
[17]	Gruber M,Azarpeyvand M,Joseph P F.Airfoil trailing edge noise reduction by the introduction of sawtooth and slitted trailing edge geometries[R].Sydney,Australia:Proceedings of 20th International Congress on Acoustics,2010.
[18]	Gruber M,Joseph P F,Chong T P.On the mechanisms of serrated airfoil trailing edge noise reduction[R].AIAA-2011-2781,2011.
[19]	Chong T P,Vathylakis A,Joseph P,et al.On the noise and wake flow of an airfoil with broken and serrated trailing edges[R].AIAA-2011-2860,2011.
[20]	Chong T P,Joseph P,Gruber M.An experimental study of airfoil instability noise with trailing edge serrations[R].AIAA-2010-3723,2010.
[21]	Chong T P,Joseph F,Gruber M.On the airfoil self-noise reduction by trailing edge serrations of non-insertion type[R].AIAA-2012-2185,2012.
[22]	Moreau D J,Doolan C J.Noise-reduction mechanism of a flat-plate serrated trailing edge[J].AIAA Journal,2013,51(10):2513-2522.
[23]	Moreau D J,Brooks L A,Doolan C J.On the noise reduction mechanism of a plate serrated trailing edge at low-to-moderate Reynolds number[R].AIAA-2012-2186,2012.
[24]	Moreau D J,Doolan C J. Tonal noise from trailing edge serrations at low Reynolds number[R].AIAA-2013-2010,2013.
[25]	Finez A,Jondeau E,Roger M,et al.Broadband noise reduction of a linear cascade with trailing edge serrations[R].AIAA-2011-2874,2011.
[26]	Tucker P G.Computation of unsteady turbomachinery flows:Part 2 LES and hybrids[J].Progress in Aerospace Sciences,2011,47(7):546-569.
[27]	罗华玲.高负荷低压涡轮叶片气动设计问题数值与实验研究[D].西安:西北工业大学,2009. LUO Hualing.Numerical and experimental investigations on aerodynamic issues of highly-loaded blading desigh in low-pressure turbine[D].Xi'an:Northwestern Polytechnical University,2009.(in Chinese)
[28]	Ventres C S,Theobald M A,Mark W D. Turbofan noise generation:Volume 1 analysis[R].NASA CR-167952,1982.